Classifications

• • B—PERFORMING OPERATIONS; TRANSPORTING
  • B64—AIRCRAFT; AVIATION; COSMONAUTICS
  • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
  • B64D15/00—De-icing or preventing icing on exterior surfaces of aircraft
  • B64D15/12—De-icing or preventing icing on exterior surfaces of aircraft by electric heating
• • G—PHYSICS
  • G08—SIGNALLING
  • G08C—TRANSMISSION SYSTEMS FOR MEASURED VALUES, CONTROL OR SIMILAR SIGNALS
  • G08C17/00—Arrangements for transmitting signals characterised by the use of a wireless electrical link
  • G08C17/04—Arrangements for transmitting signals characterised by the use of a wireless electrical link using magnetically coupled devices

Definitions

• This invention relates to rotary apparatus incorporating electrically powered devices and a method and means for controlling the supply of power to said devices.
• the invention relates to propellers incorporating a de-icing system.
• Aircraft propeller de-icing systems comprise heating devices mounted on the leading edges of propeller blades and switching means to control the application of power to these heating devices so that they are energised periodically to melt the boundary layer of ice and allow the remaining ice to break free under the effect of centrifugal and aerodynamic forces. Continuous operation of the heating devices is not desirable because this causes continuous melting of ice, which runs back onto the blade and re-freezes on aerodynamically critical working surfaces,.
• a propeller de-icing system including a permanent magnet electrical generator in the hub to supply power to a switching circuit rotating with the hub and which includes a distributor switch and the heating devices and the distributor switch is controlled by a timer on the hub, which is controlled in turn by a control signal supplied to it via a rotary connection from the aircraft on which the propeller is mounted.
• An object of the present invention is to provide an improved propeller de-icing system; in particular, a system which avoids electrical contacts between the propeller and the airframe on which it is mounted, and which allows operation of the heating devices to be monitored and controlled accordingly.
• power is switched to one or more electrically powered devices on a rotor by providing switching means on the rotor responsive to a control signal to supply power to said devices, and said control signal is supplied to the switching means via a contactless communication link between the rotor and structure on which the rotor is rotatably mounted.
• the rotor incorporates an electrical generator with inductive windings in which power is generated by rotary motion of the rotor, and the communication link comprises an inductive link incorporated in the generator.
• the communication link comprises an inductive link incorporated in the generator.
• windings may be provided on the rotor to generate an induced voltage when rotating relative to fixed magnets, and these same windings, or separate windings, may then be used as said inductive communication link by further inducing a modulated voltage or current using a control signal in a winding on the magnets.
• the control signal is preferably an encoded binary signal and the switching means includes decoding means to decode the control signal.
• control signals can be addressed to individual switching means, each controlling operation of a separate device. For example, in the case of a propeller de-icing system, the heating devices on different blades can be separately controlled.
• the same communication link or a similar link may be used to transmit performance information from the rotor to a controller, and the controller may be adapted to respond to said performance information by transmitting appropriate control signals to the switching means.
• the current and voltage in individual heating devices may be monitored and appropriate information transmitted to a de-icing controller.
• the contactless communication link between the rotor and the structure on which it is mounted comprises a radio frequency link or an optical communication link.
• Figure 1 is a schematic diagram of an aircraft propeller de- icing system according to the invention.
• Figure 2 is a schematic diagram showing the layout of components of the de-icing system of Figure 1 in relation to a propeller hub;
• Figure 3 is a schematic diagram of a power switching unit controlling the supply of power to a respective heating device in the system of Figure 1;
• Figure 4 is a schematic diagram of a single phase power switch and monitoring means of the power switching unit of Figure 3.
• Each blade has a de-icing heater 3 (Figure 1) fitted along its leading edge. Electrical power is supplied to each heater under the control of a respective power switching unit 4 which is mounted on the back-plate of the hub 1. Electrical power for the heaters 3 and switching units 4 is generated by a permanent magnet generator 5 comprising an annular array of permanent magnets 6 mounted adjacent the back-plate of the hub 1 on the engine gearbox carrying the propeller.
• Three star- connected, three phase winding 7,8,9 (Figure 1) are mounted on the back-plate of the hub 1 so that a voltage is induced therein by rotation relative to the magnets 6.
• One of these windings 7 has a 200 volt output and is connected via a bus 10 to each of the switching units 4 to provide the power supply to the heaters 3.
• Each of the other windings 8,9 has a 28 volt output and is connected via connections 11 to three of the switching units 4 to supply power to their operating circuits.
• one winding 8 supplies power to the switching units controlling power to heaters 3 on the first, third and fifth blades in the direction of rotation
• the other winding 9 supplies power to the switching units controlling power to the heaters on the second, fourth and sixth blades in the direction of rotation.
• a control unit 12 mounted on the airframe controls operation of the switching units 4 by control signals transmitted via a winding 13 on the magnets 6 which modulate the magnetic field and thus the signals induced in the windings 8 and 9.
• the control unit 12 shown in Figure 1 comprises a computer which receives control signals 13 from the aircraft and determines the operating sequence of the heaters 3.
• a driver 14 generates a high frequency output signal which is applied via connections 15 to the winding 13 on the magnets 6.
• the frequency of this output signal is varied by a frequency shift keying technique FSK under the control of a communications controller 16 so that binary control signals are transmitted via the windings 8 and 9 to the switching units 4.
• FSK frequency shift keying technique
• the communications protocol employed by the controller 16 allows it to address commands to each of the switching units 4 individually. Also, the protocol preferably incorporates error checking techniques in order to ensure safe operation.
• Each switching unit as shown in Figure 3, comprises a three phase, switching section 17, and a control section 18 which receives and decodes the control signals from the windings 8 and 9.
• a high pass filter 19 passes the FSK signal to a communications controller 20, which decodes the signal and detects commands addressed to it. Commands to operate the heaters 3 are passed to a power switch controller 21 which passes appropriate control signals to the switching section 17 via optical couplers 22.
• the switching section 17 comprises three solid state switches 23 each controlling connection of a respective phase of the power supply 7 via one of the bus conductors 10 to a respective heater 3.
• Each switch 23 comprises a pair of thyristors 24 connected back-to-back to pass current in the bus conductor 10 in either direction, control circuitry including a zero voltage detector and thyristor drive circuit 25,26,27.
• Each solid state switch 23 also incorporates a sensor winding 28 which is inductively coupled to the respective conductor 10 through which the power supply is being controlled, and this generates a corresponding sensor signal that is picked up in the monitoring circuit 29 and used to monitor the current in the bus conductor 10.
• the monitoring circuit 29 also monitors the voltage on the bus conductor 10 via a pair of electrical tappings 32.
• the monitoring circuit 29 passes the sensor signal via the optical couplers 22 to the communications controller 20 in the control section 18 of the switch 23.
• the controller 20 encodes this sensor signal in a high frequency signal using FSK and this encoded sensor signal is transmitted by a driver circuit 30 via the respective winding 8 or 9 and the winding 13 on magnets 6 back to the control unit 12 in the aircraft.
• a high pass filter 31 passes the encoded sensor signal to the communications controller 16, which decodes the signal to determine the voltage and current in the bus conductor 10.
• the control unit 12 processes the current and voltage information from the switching sections 17 of all six switching units 4 in order to monitor performance of the system and to adapt operation of the system if necessary. For example, the switching sequence of the three phases controlled by a switching unit 4 may be changed if one of the solid state switches 23 fails. Additionally, the power output for each heater 3 can be assessed and adjusted individually by controlling the on-off cycle times of the solid state switches 23 using a timer 33. In this way, the system can compensate for variations in air temperature and output of the generator 5. These sensor signals from the switching units 4 may be transmitted periodically or on demand as commanded by a control signal from the control unit 12.
• control unit 12 can be adapted to control energisation of the heaters 3 in any desired sequence to suit operating conditions.
• the rotor takes the form of an aircraft propeller with six blades and power is switched periodically to de-icing heaters on each blade.
• the propeller may have any number of blades, and the de-icing heaters may be anti-icing heaters on the blades or other de-icing or anti-icing devices such as electro expulsive and impulsive electric devices that remove ice by mechanical shock.
• the electrically powered devices on an aircraft propeller may comprise a pitch control mechanism which serves to control the pitch of one or more blades of the propeller.
• the rotor on which the electrically powered devices are mounted may comprise a vehicle wheel and the devices may comprise sensors or actuators.
• the rotor may comprise an electrical generator and the devices may comprise switches that control excitation of further generator windings.
• different modulated frequencies may be used for the communications signal.

Landscapes

• Engineering & Computer Science (AREA)
• Aviation & Aerospace Engineering (AREA)
• Computer Networks & Wireless Communication (AREA)
• Physics & Mathematics (AREA)
• General Physics & Mathematics (AREA)
• Arrangements For Transmission Of Measured Signals (AREA)
• Control Of Resistance Heating (AREA)
• Control Of Eletrric Generators (AREA)
• Apparatus For Radiation Diagnosis (AREA)
• Rotary Switch, Piano Key Switch, And Lever Switch (AREA)
• Magnetic Bearings And Hydrostatic Bearings (AREA)
• Control Of Electric Motors In General (AREA)
• Reciprocating, Oscillating Or Vibrating Motors (AREA)
• Connection Of Motors, Electrical Generators, Mechanical Devices, And The Like (AREA)

Applications Claiming Priority (3)

Publications (2)

Family

ID=10760711

Family Applications (1)

Country Status (8)

Cited By (3)

Families Citing this family (31)

Family Cites Families (13)

• 1994
  • 1994-09-02 GB GB9417639A patent/GB2293522B/en not_active Expired - Fee Related
• 1995
  • 1995-09-04 CA CA002198753A patent/CA2198753C/en not_active Expired - Fee Related
  • 1995-09-04 JP JP50929296A patent/JP3616103B2/ja not_active Expired - Fee Related
  • 1995-09-04 ES ES95930626T patent/ES2146317T3/es not_active Expired - Lifetime
  • 1995-09-04 US US08/793,694 patent/US6181235B1/en not_active Expired - Lifetime
  • 1995-09-04 DE DE69516150T patent/DE69516150T2/de not_active Expired - Fee Related
  • 1995-09-04 WO PCT/GB1995/002082 patent/WO1996007588A1/en active IP Right Grant
  • 1995-09-04 EP EP95930626A patent/EP0777602B1/de not_active Expired - Lifetime

Non-Patent Citations (1)

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